Methods and systems to facilitate reducing NOx emissions in combustion systems

Abstract

A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer wall is orientated substantially parallel to the center axis. The method also includes coupling a transition piece to the liner second end. The transition piece includes an outer wall. The method further includes coupling a plurality of lean-direct injectors along at least one of the liner outer wall and the transition piece outer wall such that the injectors are spaced axially apart along the wall.

Description

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH & DEVELOPMENT[0001]This invention was made with Government support under DE-FC26-05NT42643 awarded by the Department of Energy (“DOE”). The Government has certain rights in this inventionBACKGROUND OF THE INVENTION[0002]This invention relates generally to combustion systems and more particularly, to methods and systems to facilitate reducing NOx emissions in combustion systems.[0003]During the combustion of natural gas and liquid fuels, pollutants such as, but not limited to, carbon monoxide (“CO”), unburned hydrocarbons (“UHC”), and nitrogen oxides (“NOx”) emissions may be formed and emitted into an ambient atmosphere. CO and UHC are generally formed during combustion conditions with lower temperatures and / or conditions with an insufficient time to complete a reaction. In contrast, NOx is generally formed under higher temperatures. At least some known pollutant emission sources include devices such as, but not limited to, industrial ...

AI Technical Summary

Benefits of technology

The patent describes a way to assemble a gas turbine combustor system. It involves using a combustion liner with a center axis and an outer wall, along with a transition piece that is attached to the liner's second end. The method also involves adding a plurality of lean-direct injectors along the outer walls of both the liner and the transition piece, which are spaced apart from each other. The technical effect of this method is to improve the performance and efficiency of gas turbine combustor systems.

Problems solved by technology

The quality of fuel and air mixing in the combustor affects combustion performance.

However, at least some known lean-direct injection combustors may experience difficulties in rapid and uniform mixing of lean-fuel and rich-air within the combustor liner.

As a result, combustor components may be damaged and / or the operability of the combustor may be compromised.

Images